Gas turbine engine airfoil frequency design

1. A turbomachine airfoil element comprising:

an airfoil having pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges, the airfoil extending in a radial direction of a span that is in a range of 2.59-2.89 inch (65.7-73.3 mm);

a chord length extending in a chordwise direction from the leading edge to the trailing edge at 50% of the span is in a range of 1.35-1.65 inch (34.4-42.0 mm); and

at least two of:

a first mode has a frequency of 2241 up to ±10% Hz;

a second mode has a frequency of 3598 up to ±10% Hz; and

a third mode has a frequency of 6212 up to ±10% Hz;

wherein the frequencies are at a zero speed and ambient conditions, and the frequency of any given mode does not exceed the frequency of a higher order mode;

wherein the first mode is a 1EB mode, the second mode is a 1T mode, and the third mode is a 2T mode, the 1EB mode corresponds to deflections substantially parallel to the thickness direction, and the 1T and 2T modes correspond to twisting about the radial direction;

wherein the airfoil element is part of a stator vane having opposing ends supported by potting;

wherein the airfoil is an aluminum-based alloy, the aluminum-based alloy has a density of about 0.103 lb/in 3 (2.85 g/cm 3 ), the aluminum-based alloy has a modulus of elasticity of about 10.4 Mpsi (71 GPa) at room temperature.

2. The turbomachine airfoil element of claim 1 , wherein all of the first, second and third mode frequencies are present.

3. The turbomachine airfoil element of claim 1 , wherein at a minimum cruise speed of 8400-9400 rpm at Mach 0.8 at 35,000 feet:

the first mode has a frequency of 2177 up to ±10% Hz;

the second mode has a frequency of 3495 up to ±10% Hz; and

the third mode has a frequency of 6034 up to ±10% Hz.

4. The turbomachine airfoil element of claim 1 , wherein the frequencies are within up to ±5% ranges.

5. A method of repairing an airfoil comprising the steps of:

providing an airfoil having pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges, the airfoil extending in a radial direction of a span that is in a range of 2.59-2.89 inch (65.7-73.3 mm), and a chord length extending in a chordwise direction from the leading edge to the trailing edge at 50% of the span is in a range of 1.35-1.65 inch (34.4-42.0 mm), wherein the provided airfoil has at least one unrestored mode frequency that is attributable to damage to the airfoil; and

repairing the airfoil to provide at least two of:

a first mode has a frequency of 2241 up to ±10% Hz;

a second mode has a frequency of 3598 up to ±10% Hz; and

a third mode has a frequency of 6212 up to ±10% Hz;

wherein at least one of the first, second and third mode frequencies corresponds to a restored mode frequency that supersedes the unrestored mode frequency;

wherein the frequencies are at a zero speed and ambient conditions, and the frequency of any given mode does not exceed the frequency of a higher order mode;

wherein the first mode is a 1EB mode, the second mode is a 1T mode, and the third mode is a 2T mode, the 1EB mode corresponds to deflections substantially parallel to the thickness direction, and the 1T and 2T modes correspond to twisting about the radial direction;

wherein the airfoil element is part of a stator vane having opposing ends supported by potting;

wherein the airfoil is an aluminum-based alloy, the aluminum-based alloy has a density of about 0.103 lb/in 3 (2.85 g/cm 3 ), the aluminum-based alloy has a modulus of elasticity of about 10.4 Mpsi (71 GPa) at room temperature.

6. A turbofan engine comprising:

a fan section;

a compressor section arranged fluidly downstream from the fan section;

a turbine section arranged fluidly downstream from the compressor section;

a combustor arranged fluidly between the compressor and turbine sections; and

an airfoil in at least one of the fan, compressor and turbine sections, the airfoil having:

pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges, the airfoil extending in a radial direction of a span that is in a range of 2.59-2.89 inch (65.7-73.3 mm);

a chord length extending in a chordwise direction from the leading edge to the trailing edge at 50% of the span is in a range of 1.35-1.65 inch (34.4-42.0 mm); and

at least two of:

a first mode has a frequency of 2241 up to ±10% Hz;

a second mode has a frequency of 3598 up to ±10% Hz; and

a third mode has a frequency of 6212 up to ±10% Hz;

wherein the frequencies are at a zero speed and ambient conditions, and the frequency of any given mode does not exceed the frequency of a higher order mode;

wherein the first mode is a 1EB mode, the second mode is a 1T mode, and the third mode is a 2T mode, the 1EB mode corresponds to deflections substantially parallel to the thickness direction, and the 1T and 2T modes correspond to twisting about the radial direction;

wherein the airfoil is provided in the compressor section, the compressor section includes a high pressure compressor fluidly downstream from a low pressure compressor, and the airfoil is in the low pressure compressor and the low pressure compressor includes three stages, the airfoil element is part of a stator vane having opposing ends supported by potting;

wherein the airfoil is an aluminum-based alloy, the aluminum-based alloy has a density of about 0.103 lb/in 3 (2.85 g/cm 3 ), the aluminum-based alloy has a modulus of elasticity of about 10.4 Mpsi (71 GPa) at room temperature.